Systems and methods for landing identification

ABSTRACT

Systems and methods disclosed herein may be useful for use in landing identification. In this regard, a method is provided comprising receiving pulse information over a first time period, wherein the pulse information is indicative of an angular distance traveled by a first wheel, comparing the pulse information to a threshold value, and determining a likelihood of a landing event based upon the comparison. In various embodiments, a system is provided comprising a monstable multivibrator in electrical communication with a metal-oxide-semiconductor field-effect transistor (MOSFET), a resistor-capacitor network in electrical communication with the MOSFET, and a comparator that receives a voltage from the resistor-capacitor network and a reference voltage.

CROSS REFERENCE TO RELATED APPLICATIONS

This application is a divisional of U.S. application Ser. No.15/603,116, filed, May 23, 2017 and entitled, “Systems And Methods ForLanding Identification.” The '116 application is a divisional of U.S.application Ser. No. 13/312,495, filed, Dec. 6, 2011 and entitled,“Systems And Methods For Landing Identification.” The '495 applicationis a continuation of U.S. application Ser. No. 13/312,073, filed, Dec.6, 2011 and entitled, “Systems And Methods For Landing Identification.”The '116 application, the '495 application, and the '073 Application areeach hereby incorporated by reference in their entirety.

FIELD

The present disclosure is related to systems and methods for landingidentification for use in, for example, an aircraft.

BACKGROUND

It is useful for aircraft systems to identify or otherwise determinewhen a landing event is occurring. Many conventional aircraft identify alanding event by using signals from the landing systems, such as weighton wheels (WOW) or landing gear down lock. Thus, if the landing systemsfail, a landing event may go unidentified, and aircraft systems thatperform certain functions during landing may exhibit suboptimalperformance. Thus, there is a need for other aircraft systems to becapable of identifying a landing event. For example, it would be usefulfor an aircraft braking system to determine a landing event.

SUMMARY

Systems and methods disclosed herein may be useful for use in landingidentification. In this regard, a method is provided comprisingreceiving pulse information over a first time period, wherein the pulseinformation is indicative of an angular distance traveled by a firstwheel, comparing the pulse information to a threshold value, anddetermining a likelihood of a landing event based upon the comparison.

In various embodiments, a system is provided comprising a timer inelectrical communication with a counter, wherein the timer provides afirst time period to the counter, wherein the counter stores receivedpulse information, a comparator in electrical communication with thecounter, wherein the comparator is configured to compare the receivedpulse information with a stored value.

In various embodiments, a system is provided comprising a monstablemultivibrator in electrical communication with ametal-oxide-semiconductor field-effect transistor (MOSFET), aresistor-capacitor network in electrical communication with the MOSFET,and a comparator that receives a voltage from the resistor-capacitornetwork and a reference voltage.

In various embodiments, a method is provided comprising triggering amonstable multivibrator in response to a conditioned wheel angulardisplacement signal, sinking current, using a MOSFET, in response to thetriggering, creating an average voltage at a node from pulsed voltage ata drain of the MOSFET, and comparing, using a comparator, the averagevoltage to a reference voltage.

In various embodiments, a landing detection system is providedcomprising a wheel speed sensor that outputs a signal indicative ofangular displacement, a signal conditioner that receives the signalindicative of angular displacement and outputs a conditioned angulardisplacement signal, a monstable multivibrator that receives theconditioned angular displacement signal, wherein the monstablemultivibrator is in electrical communication with a wheel angulardisplacement circuit, wherein the wheel angular displacement circuitchanges state in response to angular displacement above a displacementthreshold over a first time period.

BRIEF DESCRIPTION OF THE DRAWINGS

Various embodiments are particularly pointed out and distinctly claimedin the concluding portion of the specification. Below is a summary ofthe drawing figures, wherein like numerals denote like elements andwherein:

FIG. 1 illustrates a landing identification system in accordance withvarious embodiments;

FIG. 2 illustrates the landing identification system of FIG. 1 andincluding a digital to analog converter, in accordance with variousembodiments;

FIG. 3 illustrates a voting scheme in accordance with variousembodiments; and

FIG. 4 illustrates a further landing identification system in accordancewith various embodiments.

DETAILED DESCRIPTION

The detailed description of exemplary embodiments herein makes referenceto the accompanying drawings, which show exemplary embodiments by way ofillustration and its best mode. While these exemplary embodiments aredescribed in sufficient detail to enable those skilled in the art topractice the inventions, it should be understood that other embodimentsmay be realized and that logical, chemical and mechanical changes may bemade without departing from the spirit and scope of the inventions.Thus, the detailed description herein is presented for purposes ofillustration only and not of limitation. For example, the steps recitedin any of the method or process descriptions may be executed in anyorder and are not necessarily limited to the order presented. Moreover,many of the functions or steps may be outsourced to or performed by oneor more third parties. Furthermore, any reference to singular includesplural embodiments, and any reference to more than one component or stepmay include a singular embodiment or step. Also, any reference toattached, fixed, connected or the like may include permanent, removable,temporary, partial, full and/or any other possible attachment option.Additionally, any reference to without contact (or similar phrases) mayalso include reduced contact or minimal contact.

Systems and methods disclosed may be useful for landing identificationsystems. Although the embodiments are described with reference tolanding identification systems used in connection with aircraft, suchembodiments are provided for example only as it is contemplated that thedisclosures herein have applicability to other vehicles, such as forexample, automobiles.

Landing identification systems that rely on wheels and/or brakes mayprovide redundancy and robustness to an aircraft's landing system-basedlanding identification system. By sourcing a landing identificationsystem in an aircraft component apart from the landing system, there isless probability of a total system failure which, in this case, would bethe failure to detect a landing. The output of landing identificationsystems may be forwarded to any aircraft component and is especiallyuseful to aircraft components that perform various functions or changetheir functionality during a landing event.

Accordingly, in various embodiments, a landing identification system maybe used to measure angular displacement of a wheel over time todetermine wheel velocity. This value may then be compared to a knownvalue, below which it is known that landing is unlikely. If the value ishigher, a voting scheme may be used amongst one or more wheels todetermine whether a landing event is occurring or if some other errorcondition is occurring. Multiple iterations may be used to verify alanding event and reduce the effect of transient anomalies and/or signalnoise.

An aircraft may comprise one or more types of aircraft wheel and brakeassemblies. For example, an aircraft may have four wheels. Two wheelsmay be on the left side of the plane and two wheels may be on the rightside of an aircraft. The left side wheels may be referred to as “leftoutboard” (LO) and “left inboard” (LI). The right side wheels may bereferred to as “right outboard” (RO) and “right inboard” (RI). Eachwheel may have its own brake assembly. The systems and methods disclosedhere may be useful in aircraft having any number of wheels.

Aircraft wheels and brake assemblies may include one or more wheel speedsensors. A wheel speed sensor may sense the speed, acceleration, and/orangular displacement of a wheel. As one should understand, the knowledgeof angular displacement over time allows one to calculate wheel speed(the scalar of angular velocity) and the knowledge of wheel speed overtime allows one to calculate acceleration of a wheel. A wheel speedsensor may be of any type, such as a Hall Effect sensor or a variablereluctance sensor.

A wheel speed sensor may output a DC voltage or an AC voltage. A wheelspeed sensor may also output a signal at a given frequency. For example,in various embodiments, a wheel speed sensor outputs a signal at fromabout 1 kHz to about 6 kHz, and more preferably at about 3 kHz. Theoutput of a wheel speed sensor may be indicative of angular displacementof a wheel. Stated another way, the output of a wheel speed sensor maycorrespond with a particular angular wheel position.

With reference to FIG. 1, landing identification system 100 is shown.Angular displacement 102 may be received by counter 104. Angulardisplacement may optionally be conditioned prior to receipt by counter104. For example, with momentary reference to FIG. 2, angulardisplacement 102 is conditioned by digital to analog convertor (DAC)202. With reference back to FIG. 1, angular displacement may beconditioned by any suitable means. Conditioning a signal may include anyalteration or modification of the signal, such as converting to a squarewave, digital conversion, or the like. Angular displacement 102, whetherconditioned or unconditioned, may be referred to as “pulse information”herein.

Counter 104 receives and stores (i.e., counts or sums) the angulardisplacement 102. Counter 104 may count any representation of angulardisplacement. Counter 104 may count peaks of a sine wave of angulardisplacement 102, zero crossings of a sine wave of angular displacement102, bits of data from a digitally converted angular displacement 102,or other suitable representation of angular displacement 102.

Timer 106 sets a period within which counter 104 counts. Timer 106 thustriggers the beginning of storage of information by counter 104 andthen, at the end of the period, triggers a purge of counter 104 so thata new period may begin. In various embodiments, timer 106 is a 555timer. The period that timer 106 sets may be of any suitable duration.In various embodiments, the duration of the period is large enough tolessen the tendency for a “false positive” due to noise or a transientangular displacement but short enough to identify a landing eventquickly. For example, in various embodiments, a period may be about 50ms to about 500 ms, more preferably, about 100 ms to about 350 ms andfurther preferably between 200 ms and 300 ms.

In various embodiments, and in response to the end of a period and/orprior to any purging of counter 104, counter 104 passes at least aportion of the information stored during the period to comparator 108.In various embodiments, a counter (e.g., counter 104) passes a numericalvalue to a comparator, where the numerical value may be, for example, areal number such as an integer. Counter 104 may pass informationindicative of the angular displacement 102 received during the period.For example, where angular displacement 102 is digital, counter 104 maysum the digital input for passing to comparator 108. For example, whereangular displacement 102 represents zero crossings, counter 104 may sumthe zero crossings for passing to comparator 108. Where counter 104outputs an analog signal, such as a voltage, counter 104 may pass avoltage to a comparator.

Comparator 108 is a digital comparator, though analog comparators may beused in various embodiments. Comparator 108 compares the value providedby counter 104 with the threshold 110. Comparator 108 outputs a firstvalue when the output of counter 104 is less than the threshold 110 andoutputs a second value when the output of counter 104 is greater than orequal to the threshold 110. It should be noted that comparator 108 maybe configured to execute any one of logical operations comprising:“greater than,” “equal to,” “less than,” “greater than or equal to,” and“less than or equal to.” Comparator 108 outputs true/false value 112.Comparator 108 is configured to output TRUE in response to the valueprovided by counter 104 being greater than or equal to the threshold 110and to output FALSE in response to the value provided by counter 104being less than threshold 110.

Threshold 110 may be set at any suitable value. Threshold 110 may beselected in accordance with the selected period. Knowledge of an amountof angular displacement along with the time period of the angulardisplacement is representative of angular velocity. Thus, threshold 110may be selected so that a comparator will output a given value inresponse to the angular velocity exceeding a particular value. Forexample, a wheel speed sensor may output a sinusoidal wave form thatcrosses the x axis (i.e., when the y axis equals 0) every time the wheelmoves one half a degree. A counter may receive two zero crossings in aperiod of, for example, 200 ms. Thus, the wheel has moved 1 degree in200 ms, and the angular velocity may be obtained by dividing the angulardisplacement over time. The threshold may then be selected to be in therange of an angular velocity associated with landing. It should beunderstood that various “bumps” or vibrations may cause a wheel torotate, but not at an angular velocity or angular acceleration that alsooccurs during landing. An aircraft may be designed to land (i.e., touchwheels to the ground) at different speeds, depending on its othercharacteristics, its intended purposes, environmental conditions, andthe like. Thus, landing may be associated with aircraft speeds of 300miles per hour and below, and more typically aircraft speeds of lessthan 200 miles per hour, various conditions may necessitate landing atmuch lower or higher speeds.

In response to comparator 108 outputting a FALSE, no action may betaken. In response to comparator 108 outputting a TRUE, a landing eventmay be identified or it may be determined that a landing event is morelikely. However, in various embodiments, a second period may elapse andan additional comparison may be performed. If another TRUE value isreceived, a landing event may be identified or it may be determined thata landing event is more likely. Thus, the likelihood of a landing eventmay be determined in response to the output of comparator 108 and/or inresponse to the output of a voting scheme, as described below.

With reference to FIG. 3, a comparator (e.g., comparator 108 of FIG. 1)may output to a voting scheme. As described above, an aircraft may havefour wheels, the LO, LI, RO, and RI. To improve the accuracy of adetermination of the likelihood of a landing event, a voting scheme maybe used to determine if more than one wheel is experiencing a givenangular velocity and/or angular acceleration. If only one wheel isexperiencing an angular velocity associated with a landing event, then afalse positive may be implicated and corrective action may need to takeplace. If multiple wheels are experiencing an angular velocityassociated with a landing event, then a landing event is more likely,and if all wheels are experiencing an angular velocity associated with alanding event, then a landing event is more likely still.

Voting scheme 300 includes inputs LO 302, LI 304, RO 306, and RI 308.Each input LO 302, LI 304, RO 306, and RI 308 may be produced bycomponents such as those shown in FIGS. 1 and 2. Stated another way,inputs LO 302, LI 304, RO 306, and RI 308 comprise TRUE or FALSE valuesthat are indicative of an angular velocity above a threshold amount.

LO 302 and LO 304 are in electrical communication with AND gate 310. ANDgate 310 is configured to output TRUE when LO 302 and LO 304 are bothTRUE. RO 306 and RO 308 are in electrical communication with AND gate314. AND gate 314 is configured to output TRUE when RO 306 and RO 308are both TRUE.

AND gate 310 and AND gate 314 are in electrical communication with ANDgate 312. AND gate 312 is configured to output TRUE when both AND gate310 and AND gate 314 are true. Other aircraft components may note thatin response to AND gate 312 being true, a landing event is occurringand, conversely, aircraft components may note that in response to ANDgate 312 being false, a landing event is not occurring. Thus, votingscheme 300 illustrates an embodiment where four wheels must observe asufficient angular velocity before a landing event is identified. Invarious embodiments, only one or more wheels would be needed to indicatea landing event. For example, if AND gate 310 and AND gate 314 werereplaced with OR gates, only one wheel on each side of the aircraftwould need to observe a landing event for AND gate 310 to output TRUE.Any other implementation may be used to select which wheel and how manywheels must observe a landing event in order for the system to indicatea landing event.

Landing detection systems may also be implemented in a circuitcomprising at least one of a monostable mulivibrator, a referencevoltage, MOSFET and a resistor-capacitor network. Such circuits mayprovide a reduced tendency for false positives due to its ability todisregard signal noise and/or transient movement of the wheel.

With reference to FIG. 4, landing detection system 400 is shown. Angulardisplacement signal 402 is input into signal conditioner 404. Signalconditioner 404 may comprise any signal conditioning step and/or noconditioning at all. For example, signal conditioner 404 may condition asinusoidal wave form into a square waveform. Signal conditioner 404 mayrectify an AC signal into a DC signal. Signal conditioner 404 may outputa conditioned signal.

One shot 406 is a monostable multivibrator. A monostable multivibratormay be used to set a time period in response to a triggering event. Invarious embodiments, the conditioned signal from signal conditioner 404may be used as a triggering event. For example, the rising or fallingedge of the conditioned signal from signal conditioner 404 may be usedas a triggering event. In that regard, one shot 406 begins a period upona fixed conditioned signal.

In various embodiments, a one shot may be in electrical communicationwith a wheel angular displacement circuit. A wheel angular displacementcircuit may comprise one or more components that may evaluate theconditioned signal from signal conditioner 404 and change output statein accordance with the conditioned signal from signal conditioner 404.For example, a wheel angular displacement circuit may be configured toevaluate a conditioned signal against a reference voltage, for example,and the wheel angular displacement circuit's may change output statebased upon the evaluation. In various embodiments, a wheel angulardisplacement circuit may evaluate a conditioned signal against areference voltage and change output voltage in accordance with theevaluation.

With reference back to FIG. 4, a wheel angular displacement circuit isillustrated comprising, among other components, MOSFET 408, theillustrated voltage follower, comparator 410, and a resistor-capacitornetwork.

MOSFET 408 is a metal-oxide-semiconductor field-effect transistor,though other transistors that provide the same or similar functionalityare contemplated herein. The triggering of one shot 406 turns on MOSFET408, which sinks current for the duration or part of the duration of theperiod of one shot 406.

A resistor-capacitor network is shown comprising R1, R2, C1 and C2. Theresistor-capacitor network is configured to create an average voltage atnode A from the pulsed voltage at the drain of the MOSFET 408. Otherconfigurations of R1, R2, C1 and C2 are contemplated herein, includingthe addition of other components.

The voltage follower may be in electrical communication with theresistor-capacitor network. The voltage follower may create a buffer toisolate the comparator 410. R4 and R5 are in electrical communicationwith the voltage follower. R4 is connected to the negative terminal ofcomparator 410 and R5 is wired in series with R4 as illustrated. R4 andR5 provide hysteresis functionality to comparator 410. In variousembodiments, however, comparator 410 may be selected to have adequateinternal hysteresis and, thus, the voltage follower and R4 and R5 may beomitted.

As the input frequency increases, the duty cycle of MOSFET 408increases, which in turn causes the average voltage at node A todecrease. When the frequency crosses a desired threshold, the duty cycleof MOSFET 408 may be sufficient to pull the input voltage to comparator410 below the reference voltage (V_(ref)). Comparator 410 will thenchange outputs, indicating that the threshold of V_(ref) has beenexceeded. In that regard, the threshold may be controlled by the pulsewidth of one shot 406, V_(ref), and the selection of V+.

Voting schemes, such voting scheme 300 of FIG. 3, may be used inconnection with embodiments such as that described in FIG. 4.

Systems, methods and computer program products are provided. In thedetailed description herein, references to “one embodiment”, “anembodiment”, “an example embodiment”, etc., indicate that the embodimentdescribed may include a particular feature, structure, orcharacteristic, but every embodiment may not necessarily include theparticular feature, structure, or characteristic. Moreover, such phrasesare not necessarily referring to the same embodiment. Further, when aparticular feature, structure, or characteristic is described inconnection with an embodiment, it is submitted that it is within theknowledge of one skilled in the art to effect such feature, structure,or characteristic in connection with other embodiments whether or notexplicitly described. After reading the description, it will be apparentto one skilled in the relevant art(s) how to implement the disclosure inalternative embodiments.

Benefits, other advantages, and solutions to problems have beendescribed herein with regard to specific embodiments. However, thebenefits, advantages, solutions to problems, and any elements that maycause any benefit, advantage, or solution to occur or become morepronounced are not to be construed as critical, required, or essentialfeatures or elements of the inventions. The scope of the inventions isaccordingly to be limited by nothing other than the appended claims, inwhich reference to an element in the singular is not intended to mean“one and only one” unless explicitly so stated, but rather “one ormore.” Moreover, where a phrase similar to “at least one of A, B, or C”is used in the claims, it is intended that the phrase be interpreted tomean that A alone may be present in an embodiment, B alone may bepresent in an embodiment. C alone may be present in an embodiment, orthat any combination of the elements A. B and C may be present in asingle embodiment; for example, A and B, A and C, B and C, or A and Band C. Furthermore, no element, component, or method step in the presentdisclosure is intended to be dedicated to the public regardless ofwhether the element, component, or method step is explicitly recited inthe claims. No claim element herein is to be construed under theprovisions of 35 U.S.C. 112, sixth paragraph, unless the element isexpressly recited using the phrase “means for.” As used herein, theterms “comprises”, “comprising”, or any other variation thereof, areintended to cover a non-exclusive inclusion, such that a process,method, article, or apparatus that comprises a list of elements does notinclude only those elements but may include other elements not expresslylisted or inherent to such process, method, article, or apparatus.

The invention claimed is:
 1. A method for landing identificationcomprising: triggering a monstable multivibrator in response to aconditioned wheel angular displacement signal; sinking current, using ametal-oxide-semiconductor field-effect transistor (MOSFET), in responseto the triggering; creating an average voltage at a node from pulsedvoltage at a drain of the MOSFET; comparing, using a comparator, theaverage voltage to a reference voltage; and determining a likelihood ofa landing event based upon the comparison.
 2. The method of claim 1,further comprising conditioning a wheel angular displacement to obtainthe conditioned wheel angular displacement signal.
 3. The method ofclaim 1, further comprising buffering the comparator using a voltagefollower.
 4. The method of claim 1, wherein the creating the averagevoltage is performed by a resistor-capacitor network.
 5. The method ofclaim 1, further comprising adding hysteresis to the comparator using aresistor.
 6. The method of claim 1, further comprising increasing a dutycycle of the MOSFET.
 7. The method of claim 6, further comprisingdecreasing, in response to the increase in the duty cycle of the MOSFET,the average voltage.